CN109736953B - Multi-start liquid oxygen kerosene engine of gas-driven pre-compressed turbine and starting method - Google Patents
Multi-start liquid oxygen kerosene engine of gas-driven pre-compressed turbine and starting method Download PDFInfo
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- CN109736953B CN109736953B CN201811527846.5A CN201811527846A CN109736953B CN 109736953 B CN109736953 B CN 109736953B CN 201811527846 A CN201811527846 A CN 201811527846A CN 109736953 B CN109736953 B CN 109736953B
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Abstract
The invention relates to a multiple-start liquid oxygen kerosene engine of a gas-driven pre-pressing turbine, which aims to solve the problems that an oxygen-enriched afterburning circulating liquid oxygen kerosene engine does not have the starting capability under the condition of low inlet pressure and can not be started for multiple times; the starting system comprises a high-pressure gas supply device, a high-pressure gas one-way valve, an oxygen pre-pressurizing pump, an oxygen pre-pressurizing turbine, a switching valve, a liquid oxygen one-way valve and a blender; the igniter starting box of the liquid oxygen kerosene engine is relatively independent, and can provide the igniter for the fuel gas generator and the thrust chamber for multiple times, so that the engine has the capability of starting for multiple times.
Description
Technical Field
The invention belongs to the field of liquid oxygen kerosene engines, and relates to a liquid oxygen kerosene engine and a starting method thereof.
Background
The liquid oxygen kerosene engine is a high-performance and high-reliability liquid propulsion device. The starting energy is generally guaranteed by the tank pressure or by an external energy source drive; providing an ignition medium to the gas generator and the thrust chamber by providing an igniter conduit; and arranging corresponding valves to coordinate the coordination work of all the components. When the engine is used as a high-altitude multi-start propelling device, the pressure of an oxidant storage tank and a fuel storage tank is low, and the engine is required to have the starting capability under the condition of low inlet pressure; to meet the requirement of multiple starts, the engine is required to have multiple ignition capabilities.
The starting modes of the engine at present include a self-generating starting mode and a forced starting mode.
If the mode of self-generation starting is adopted, the amount of the propellant entering the engine at the initial starting stage is small due to the low pressure of the storage tank, so that enough starting energy cannot be ensured, and meanwhile, the inlet pressure of the oxygen main pump is low, so that cavitation is easy to occur.
On one hand, the consumption of external media is large because the power of the main turbine, the oxygen main pump, the fuel primary pump and the fuel secondary pump is high; on the other hand, the flow rate of the starting section is changed rapidly, so that the oxygen main pump is easy to generate cavitation under the condition of low inlet pressure.
The existing supply mode of the ignition agent of the engine is generally realized by arranging an ignition agent guide pipe in a fuel supply pipeline, and the supply mode of the ignition agent can only be used for one time or two to three times of ignition and cannot be used for multiple times of ignition.
Disclosure of Invention
The invention provides a multi-start liquid oxygen kerosene engine with a gas-driven pre-pressure turbine and a starting method thereof, aiming at solving the problems that an oxygen-enriched afterburning circulating liquid oxygen kerosene engine does not have the starting capability under the condition of low inlet pressure and can not be started for multiple times.
The technical solution of the invention is as follows:
the invention relates to a multi-start liquid oxygen kerosene engine of a gas-driven pre-compressed turbine, which comprises a gas system, a liquid oxygen system, a fuel supply system, an igniter supply system and a starting system;
the gas system comprises a gas generator 11, a main turbine 12 and a thrust chamber 13 which are connected in sequence;
the liquid oxygen system comprises an oxygen main pump 21 and a liquid oxygen main valve 22, wherein the oxygen main pump 21 is coaxially arranged with the main turbine 12, the oxygen main pump 21 is connected with a liquid oxygen inlet of the gas generator 11 through a first pipeline 23, and the liquid oxygen main valve 22 is arranged in the first pipeline 23;
it is characterized in that:
the igniter supply system comprises an igniter starting box 31, an igniter supply valve 32, a third one-way valve 33, a generator fuel valve 34 and a fourth one-way valve 35, wherein the generator fuel valve 34 is a two-position three-way valve and comprises an inlet, an outlet A and an outlet B;
the inlet of the ignition agent starting box 31 is connected with the ignition agent extrusion gas, the outlet of the ignition agent starting box is connected with the fuel inlet of the generator fuel valve 34 through a second pipeline 36, the ignition agent supply valve 32 and a third one-way valve 33 are arranged on the second pipeline 36, and the ignition agent supply valve 32 is arranged on the pipeline upstream of the third one-way valve 33;
an outlet A of the generator fuel valve 34 is communicated with an ignition path inlet of the gas generator 11, and an outlet B of the generator fuel valve 34 is communicated with an ignition path inlet of the thrust chamber 13 through a third pipeline 37; the fourth check valve 35 is arranged in the third line 37;
the fuel supply system comprises a fuel primary pump 41, a fuel secondary pump 42, a thrust chamber fuel main valve 43, a first check valve 44 and a second check valve 46; the thrust chamber fuel main valve 43 is a two-position three-way valve and comprises an inlet, an outlet A and an outlet B;
the fuel primary pump 41 and the fuel secondary pump 42 are coaxially arranged with the main turbine 12;
the inlet of the primary fuel pump 41 is communicated with the outlet of the fuel storage tank, and the outlet of the primary fuel pump 41 is connected with the inlet of the secondary fuel pump 42 through a fourth pipeline 45;
the outlet of said secondary fuel pump 42 is connected to the second line 36 by a fifth line 47, downstream of the outlet of the third non-return valve 33, said second non-return valve 46 being arranged in the fifth line 47;
the outlet of the primary fuel pump 41 is also connected to the third line 37 by a sixth line 48, between the outlet B of the generator fuel valve 34 and the inlet of the fourth check valve 35, the first check valve 44 being located in the sixth line 48;
the outlet of the primary fuel pump 41 is also connected to the main fuel inlet of the thrust chamber 13 through a seventh pipeline 49, and the main fuel valve 43 of the thrust chamber is arranged in the seventh pipeline 49;
the starting system comprises a high-pressure gas supply device, a high-pressure gas one-way valve 51, an oxygen pre-pressurizing pump 52, an oxygen pre-pressurizing turbine 53, a switching valve 54, a liquid oxygen one-way valve 55 and a blender 56;
the high-pressure gas supply device is connected with the inlet of the oxygen pre-pressurizing turbine 53 through an eighth pipeline 57, and the high-pressure gas one-way valve 51 is arranged on the eighth pipeline 57;
the oxygen precompression pump 52 and the oxygen precompression turbine 53 are coaxially arranged; the inlet of the oxygen pre-pressurizing pump 52 is communicated with the outlet of the oxidant storage tank, and the outlet of the oxygen pre-pressurizing pump 52 is connected with the inlet of the oxygen main pump 21 through a ninth pipeline 58; the blender 56 is disposed on a ninth line 58;
the inlet of the oxygen pre-pressure turbine 53 is connected with the first pipeline 23 through a tenth pipeline 59, and the connection position is between the outlet of the oxygen main pump 21 and the inlet of the liquid oxygen main valve 22; the outlet of the oxygen pre-compression turbine 53 is connected to the blender 56 through an eleventh pipe 60;
the liquid oxygen check valve 55 is disposed in the tenth pipe 59;
the switching valve 54 is a two-position three-way valve and comprises an inlet, an outlet A and an outlet B, the switching valve 54 is connected to the eleventh pipeline 60 through the inlet and the outlet A, and the outlet B is communicated with the outside.
Further, a first throttling ring 61 is arranged on a pipeline between the outlet of the ignition agent supply valve 32 and the inlet of the third one-way valve 33.
Further, a second throttle washer 62 is arranged on a pipeline between the outlet of the fourth check valve 35 and the ignition inlet of the thrust chamber 13.
Further, a third throttling ring 63 is arranged on a pipeline between the outlet of the primary fuel pump 41 and the inlet of the first check valve 44.
Further, a fourth throttling ring 64 is arranged on a pipeline between the outlet of the third one-way valve 33 and the generator fuel valve 34.
Meanwhile, the invention also provides a starting method of the liquid oxygen kerosene engine which is started for multiple times by the gas-driven pre-pressing turbine, which is characterized by comprising the following steps:
(1) liquid oxygen and fuel fill
Before the engine is started, the liquid oxygen system is precooled and filled, and the oxidant is discharged to the outside from the liquid oxygen main valve 22;
the fuel system is vacuumized and filled with fuel, and the fuel is discharged to the outside from a thrust chamber fuel main valve 43;
(2) ignition agent charge
Starting, the high-pressure gas presses the igniting agent starting box 31, simultaneously opens the igniting agent supplying valve 32, the igniting agent fills the igniting path of the fuel gas generator 11 and the igniting path of the thrust chamber 13 through the third one-way valve 33, the generator fuel valve 34 and the fourth one-way valve 35;
(3) after the ignition path of the thrust chamber 13 is completed by filling the ignition agent, a control instruction is sent to the switching valve 54, and the outlet of the oxygen pre-pressurizing turbine 53 is communicated with the outside;
(4) supplying high-pressure gas, wherein the gas enters a gas static cavity of an oxygen pre-pressurizing turbine 53 through a high-pressure gas one-way valve 51, the oxygen pre-pressurizing turbine 53 is driven to do work, so that the oxygen pre-pressurizing pump 52 generates a positive lift, and the pressurized liquid oxygen is discharged from a discharge port of a liquid oxygen main valve 22;
(5) the liquid oxygen main valve 22 is opened, and liquid oxygen is filled in the oxygen head cavity of the fuel gas generator;
(6) the generator fuel valve 34 is opened, the igniter enters the gas generator 11 at a certain flow rate, the gas generator 11 generates gas, and the gas drives the main turbine 12 to work;
(7) as the rotation speed of the main turbine 12, the oxygen main pump 21, the fuel primary pump 41 and the fuel secondary pump 42 rises, when the pressure behind the fuel secondary pump 42 rises to be greater than the opening pressure of the second check valve 46, kerosene enters the generator fuel path, the igniter starting box 31 stops supplying the igniter, and then the igniter extrudes gas to be exhausted;
when the pressure after the fuel primary pump 41 rises to be larger than the opening pressure of the first check valve 44, the kerosene enters the ignition path of the thrust chamber 13;
when the pressure behind the oxygen main pump 21 is greater than the opening pressure of the liquid oxygen check valve 55 of the driving path of the oxygen pre-pressurizing turbine 53, liquid oxygen enters the liquid static cavity of the oxygen pre-pressurizing turbine 53 and drives the oxygen pre-pressurizing turbine 53 to do work together with high-pressure gas;
(8) the high-pressure gas supply is cut off, and the high-pressure liquid oxygen behind the oxygen main pump 21 continues to drive the oxygen pre-pressurizing turbine 53 to do work;
(9) the switching valve 54 is reset, and high-pressure liquid oxygen after the oxygen main pump 21 enters the blender 56 after driving the oxygen pre-pressurizing turbine 53, and enters the inlet of the oxygen main pump 21 after being blended with liquid oxygen after the oxygen pre-pressurizing pump 52;
(10) determining the opening time of the fuel main valve 43 of the thrust chamber according to the filling time of the thrust chamber 13, and igniting the thrust chamber 13 after the residual power of the main turbine 12, the oxygen main pump 21, the fuel primary pump 41 and the fuel secondary pump 42 is enough to generate positive feedback on the power of the main turbine 12, the oxygen main pump 21, the fuel primary pump 41 and the fuel secondary pump 42;
(11) the engine gradually enters the primary operating condition.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the liquid oxygen kerosene engine started for multiple times by the gas-driven pre-pressure turbine and the starting method, the high-pressure gas drives the oxygen pre-pressure turbine, so that the oxygen pre-pressure pump generates a positive lift, and the anti-cavitation capability of the main pump is improved; and simultaneously, the flow of the oxidant entering the fuel gas generator at the starting section is ensured, so that the engine has enough starting energy.
2. The igniter starting box of the gas-driven pre-compressed turbine multi-time starting liquid oxygen kerosene engine is relatively independent, and can provide the igniter for the fuel gas generator and the thrust chamber for multiple times, so that the engine has the capability of multi-time starting.
3. The liquid oxygen kerosene engine for multiple starting of the gas-driven pre-compressed turbine adopts a plurality of two-position three-way valves, the valve function integration level is high, and the system is simplified.
4. The liquid oxygen kerosene engine with multiple starts of the gas-driven pre-pressing turbine can ensure the ignition flow of the generator and the thrust chamber by optimizing the flow resistance and the position of the throttling ring, thereby optimizing the ignition conditions of the generator and the thrust chamber.
5. The starting energy of the liquid oxygen kerosene engine which is started for multiple times and is driven by the gas is determined by the power of the high-pressure gas, the supercharging pressure of the rocket body storage box is reduced, and the technical difficulty of the rocket body is reduced.
6. The liquid oxygen kerosene engine started for multiple times by the gas-driven pre-compressed turbine has the advantages that the pre-compressed turbine pump has low power, so that the high-pressure gas consumption is obviously reduced, the volume of a gas cylinder is reduced, and the carrying capacity is improved.
Drawings
FIG. 1 is a schematic structural diagram of a multi-start liquid oxygen kerosene engine with a gas-driven pre-compressed turbine according to an embodiment of the invention.
Wherein the reference numerals are: 11-gas generator, 12-main turbine, 13-thrust chamber, 21-oxygen main pump, 22-liquid oxygen main valve, 23-first pipeline, 31-ignition agent starting box, 32-ignition agent supply valve, 33-third one-way valve, 34-generator fuel valve, 35-fourth one-way valve, 36-second pipeline, 37-third pipeline, 41-fuel primary pump, 42-fuel secondary pump, 43-thrust chamber fuel main valve, 44-first one-way valve, 45-fourth pipeline, 46-second one-way valve, 47-fifth pipeline, 48-sixth pipeline, 49-seventh pipeline, 51-high pressure gas one-way valve, 52-oxygen pre-pressurizing pump, 53-oxygen pre-pressurizing turbine, 54-switching valve, 55-liquid oxygen one-way valve, 56-blender, 57-eighth line, 58-ninth line, 59-tenth line, 60-eleventh line. 61-first throttle ring, 62-second throttle ring, 63-third throttle ring, 64-fourth throttle ring.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
First, system configuration
The structure of the multi-start liquid oxygen kerosene engine of the gas-driven pre-pressure turbine is shown in figure 1. The engine comprises the following subsystems:
1. a gas system. The gas system mainly provides oxygen-enriched gas for the thrust chamber. The method comprises the following steps: are connected in sequence
A gas generator 11, a main turbine 12, a thrust chamber 13, etc.
2. Liquid oxygen system. The liquid oxygen system is mainly used for supplying high-pressure liquid oxygen to the fuel gas generator. The method comprises the following steps: the main oxygen pump 21 is coaxially arranged with the main turbine 12, the main oxygen pump 21 is connected with the liquid oxygen inlet of the gas generator 11 through a first pipeline 23, and the liquid oxygen main valve 22 is arranged in the first pipeline 23.
3. An igniter supply system. The igniter supply system functions to supply an igniter to the thrust chamber and the gas generator. The ignition agent starting box comprises an ignition agent starting box 31, an ignition agent supply valve 32, a third one-way valve 33, a generator fuel valve 34 and a fourth one-way valve 35, wherein the generator fuel valve 34 is a two-position three-way valve and comprises an inlet, an outlet A and an outlet B; the outlet of the ignition agent starting tank 31 is connected with the fuel inlet of the generator fuel valve 34 through a second pipeline 36, the ignition agent supply valve 32 and the third check valve 33 are arranged on the second pipeline 36, and the ignition agent supply valve 32 is arranged on the pipeline upstream of the third check valve 33; the outlet A of the generator fuel valve 34 is communicated with the ignition path inlet of the gas generator 11, and the outlet B of the generator fuel valve 34 is communicated with the ignition path inlet of the thrust chamber 13 through a third pipeline 37; a fourth check valve 35 is provided in the third line 37; the igniter starter box has the capability of storing triethylaluminum and triethylboron igniters for a long time, is physically isolated from the extrusion gas, and can be extruded for multiple times.
The generator fuel valve is in the initial state that the inlet is communicated with the outlet B and is cut off from the outlet A; when a control command is given to the generator fuel valve, the inlet is communicated with the outlet A, and the outlet B is cut off.
The igniting agent supply valve is a normally closed valve, and an inlet is communicated with an outlet of the igniting agent starting box; the outlet is communicated with the outlet pipeline of the fuel secondary pump. The ignition agent starting tank supplies the ignition agent to the fuel secondary pump outlet line when the ignition agent supply valve is open.
The third one-way valve is responsible for preventing the fuel of the outlet of the fuel secondary pump from entering the ignition agent starting box in the stable section, and simultaneously, the ignition agent is provided for the thrust chamber ignition path and the generator ignition path by the ignition agent starting box in the starting section.
The fourth one-way valve is responsible for supplying fuel to the ignition nozzle of the thrust chamber in the stable section and supplying the ignition agent to the ignition nozzle of the thrust chamber in the starting section, and simultaneously preventing the fuel gas of the thrust chamber from flowing back to a fuel system.
4. Fuel supply system the fuel supply system is mainly to supply high pressure kerosene to the thrust chamber and the generator. The method comprises the following steps: comprises a fuel primary pump 41, a fuel secondary pump 42, a thrust chamber fuel main valve 43, a first check valve 44 and a second check valve 46; the main thrust chamber fuel valve 43 is a two-position three-way valve including an inlet, an outlet a, and an outlet B. The primary fuel pump 41 and the secondary fuel pump 42 are coaxially arranged with the main turbine 12; the inlet of the primary fuel pump 41 is communicated with the outlet of the fuel storage tank, and the outlet of the primary fuel pump 41 is connected with the inlet of the secondary fuel pump 42 through a fourth pipeline 45; the outlet of the secondary fuel pump 42 is connected to the second line 36 by a fifth line 47, downstream of the outlet of the third non-return valve 33, a second non-return valve 46 being arranged in the fifth line 47; the outlet of the primary fuel pump 41 is also connected to the third line 37 by a sixth line 48, between the outlet B of the generator fuel valve 34 and the inlet of the fourth check valve 35, the first check valve 44 being located in the sixth line 48; the outlet of the primary fuel pump 41 is also connected to the main fuel inlet of the thrust chamber 13 via a seventh conduit 49, and a main thrust chamber fuel valve 43 is provided in the seventh conduit 49.
The first check valve is responsible for supplying propellant from the fuel primary pump outlet to the thrust chamber ignition circuit in the stabilizing section while preventing the reverse flow of the ignition agent to the fuel primary pump outlet in the starting section.
The second check valve is responsible for supplying fuel from the fuel secondary pump outlet to the gas generator during the stabilization phase while preventing the back-bleeding of the ignition agent to the fuel secondary pump outlet during the start phase.
5. The system is started. The starting system is used for increasing the inlet pressure of the oxygen main pump in the starting section and providing enough energy for the rotation of the main turbine, and comprises a high-pressure gas supply device, a high-pressure gas one-way valve 51, an oxygen pre-pressurizing pump 52, an oxygen pre-pressurizing turbine 53, a switching valve 54, a liquid oxygen one-way valve 55 and a blender 56; the high-pressure gas supply device is connected with the inlet of the oxygen pre-pressurizing turbine 53 through an eighth pipeline 57, and the high-pressure gas check valve 51 is arranged on the eighth pipeline 57; the oxygen precompression pump 52 is arranged coaxially with the oxygen precompression turbine 53; the inlet of the oxygen pre-pressure pump 52 is communicated with the outlet of the oxidant storage tank, and the outlet of the oxygen pre-pressure pump 52 is connected with the inlet of the oxygen main pump 21 through a ninth pipeline 58; the blender 56 is disposed on a ninth conduit 58; the inlet of the oxygen pre-pressure turbine 53 is connected with the first pipeline 23 through a tenth pipeline 59, and the connection position is between the outlet of the oxygen main pump 21 and the inlet of the liquid oxygen main valve 22; the outlet of the oxygen pre-compression turbine 53 is connected to the blender 56 through an eleventh line 60;
the switching valve 54 is a two-position three-way valve for switching the medium at the valve inlet to communicate with the inlet pipeline of the oxygen main pump or to discharge to the outside. The inlet is connected with an outlet pipeline of the oxygen pre-pressing turbine, the outlet A is connected with a blender at the inlet of the oxygen main pump, and the outlet B is connected with the outside. In the initial state, the inlet medium of the valve is normally communicated with the outlet A, and the outlet B is cut off; after the control command is sent out, the inlet is communicated with the outlet B, and the outlet A is cut off.
Second, system matching
Key matching conditions:
1. the inlet pressure and the flow of the high-pressure gas need to ensure enough flow generated by the starting section oxygen pre-pressing turbine pump, and the flow is based on ensuring that the flow of the oxygen-enriched gas generated by the ignition of the generator can meet the requirement of the residual power of the starting section turbine pump;
2. the liquid oxygen one-way valve from the outlet of the oxygen main pump to the oxygen pre-pressing turbine driving path requires that the reverse sealing performance is good enough, and gas at the outlet of the starting section oxygen pre-pressing turbine is prevented from entering a liquid oxygen system; the pressure of the outlet of the oxygen main pump is required to be opened after being higher than a certain value, so that the liquid oxygen at the outlet of the oxygen main pump does not enter the static cavity of the oxygen pre-pressing turbine at the initial working stage of high-pressure gas.
3. The ignition agent is supplied by an ignition agent starting box, throttle rings are arranged at an outlet of the ignition agent starting box, a generator fuel path and a thrust chamber ignition path, and the matching of the flow rate of the ignition agent at the starting section and the oxygen flow rate at the starting section and the matching of the flow rate of the generator fuel at the stable section and the oxygen flow rate of the generator at the stable section are respectively ensured through matching parameters. So that the ignition temperature peak of the generator in the starting section does not exceed 1000K, and the generator temperature in the stable section does not exceed 850K.
4. The opening pressure of the first check valve and the second check valve is high enough to ensure that the kerosene cannot enter the gas generator and the thrust chamber ignition path in the ignition agent filling section.
5. The main thrust chamber fuel valve opens when the main turbine, oxygen main pump, fuel primary pump and fuel secondary pump generate sufficient surplus power.
The invention relates to a starting method of a liquid oxygen kerosene engine which is started for multiple times and provided with a gas-driven pre-compressed turbine, which comprises the following steps:
1. before the engine is started, the liquid oxygen system is pre-cooled and filled, and the oxidant is discharged to the outside from the liquid oxygen main valve. The fuel system is vacuumized and filled with fuel, and the fuel is discharged to the outside from a fuel main valve of the thrust chamber;
2. starting is performed by first filling the ignition agent. The igniter extruding gas extrudes the igniter starting box, simultaneously opens the igniter supply valve, and the igniter fills the generator ignition path and the thrust chamber ignition path through the third check valve, the generator fuel valve and the fourth check valve. The ignition agent charging time is determined by the pressure of the high-pressure extrusion gas and the throttle ring in the ignition agent charging flow path.
The first check valve is arranged at the outlet of the fuel first-stage pump, and the second check valve is arranged at the outlet of the fuel second-stage pump, so that on one hand, the opening pressure is ensured to be high enough, and kerosene is prevented from entering the generator and the thrust chamber ignition path before the ignition agent is filled; and on the other hand, reverse sealing prevents the ignition agent from entering the fuel primary pump and the fuel secondary pump chamber.
3. After the ignition agent is filled in the ignition path of the thrust chamber. Sending a control instruction to the switching valve, wherein the outlet of the oxygen pre-pressing turbine is communicated with the outside;
4. supplying high-pressure gas, wherein the gas enters the gas static cavity of the oxygen pre-pressing turbine through the high-pressure gas one-way valve to drive the oxygen pre-pressing turbine to do work, so that the oxygen pre-pressing pump generates a positive lift, and the pressurized liquid oxygen is discharged from a discharge port of the liquid oxygen main valve;
5. opening a liquid oxygen main valve, and filling liquid oxygen into an oxidant cavity of the fuel gas generator;
6. the fuel valve of the generator is opened, the igniting agent enters the generator at a certain flow rate, and the supply of the igniting agent of the ignition path of the thrust chamber is cut off;
7. along with the increase of the rotating speed of the main turbine, the oxygen main pump, the fuel primary pump and the fuel secondary pump, when the outlet pressure of the fuel secondary pump is increased to be larger than the opening pressure of the second one-way valve, kerosene enters a fuel path of the generator, the igniter starting box stops supplying the igniter, and then the igniter extrudes gas to remove the gas; when the outlet pressure of the fuel primary pump is increased to be larger than the opening pressure of the first one-way valve, kerosene enters the thrust chamber ignition circuit, and the cavity of the ignition circuit and the opening pressure of the first one-way valve jointly ensure that enough ignition agent is still available to maintain the ignition of the thrust chamber when the thrust chamber is ignited; when the outlet pressure of the oxygen main pump is higher than the opening pressure of a liquid oxygen one-way valve of the oxygen pre-pressing turbine driving path, liquid oxygen enters a liquid static cavity of the oxygen pre-pressing turbine and drives the oxygen pre-pressing turbine to work together with high-pressure gas;
8. the high-pressure gas supply path of the oxygen pre-pressing turbine is cut off, and the high-pressure liquid oxygen at the outlet of the oxygen main pump continues to drive the oxygen pre-pressing turbine to do work;
9. the switching valve is reset, high-pressure liquid oxygen at the outlet of the oxygen main pump enters the blender after driving the oxygen pre-pressing turbine, and enters the inlet of the oxygen main pump after being blended with liquid oxygen at the outlet of the oxygen pre-pressing pump;
10. determining the opening time of a fuel main valve of the thrust chamber according to the filling time of the thrust chamber, so that the thrust chamber is ignited after the residual power of the main turbine, the oxygen main pump, the fuel primary pump and the fuel secondary pump is enough to generate positive feedback on the power of the main turbine, the oxygen main pump, the fuel primary pump and the fuel secondary pump;
the engine is gradually brought into a steady operating condition 11.
Claims (6)
1. The liquid oxygen kerosene engine with gas driven pre-compressed turbine for starting several times includes gas system, liquid oxygen system, fuel supply system, igniter supply system and starting system;
the gas system comprises a gas generator (11), a main turbine (12) and a thrust chamber (13) which are connected in sequence;
the liquid oxygen system comprises an oxygen main pump (21) and a liquid oxygen main valve (22), wherein the oxygen main pump (21) is coaxially arranged with a main turbine (12), the oxygen main pump (21) is connected with a liquid oxygen inlet of the gas generator (11) through a first pipeline (23), and the liquid oxygen main valve (22) is arranged in the first pipeline (23);
the method is characterized in that:
the igniter supply system comprises an igniter starting box (31), an igniter supply valve (32), a third one-way valve (33), a generator fuel valve (34) and a fourth one-way valve (35), wherein the generator fuel valve (34) is a two-position three-way valve and comprises an inlet, an outlet A and an outlet B;
the inlet of the ignition agent starting box (31) is connected with the ignition agent extrusion gas, the outlet of the ignition agent starting box is connected with the fuel inlet of a fuel valve (34) of the generator through a second pipeline (36), the ignition agent supply valve (32) and a third one-way valve (33) are arranged on the second pipeline (36), and the ignition agent supply valve (32) is arranged on the pipeline upstream of the third one-way valve (33);
the outlet A of the generator fuel valve (34) is communicated with the ignition path inlet of the fuel gas generator (11), and the outlet B of the generator fuel valve (34) is communicated with the ignition path inlet of the thrust chamber (13) through a third pipeline (37); the fourth non-return valve (35) is arranged in a third line (37);
the fuel supply system comprises a fuel primary pump (41), a fuel secondary pump (42), a thrust chamber fuel main valve (43), a first check valve (44) and a second check valve (46); the thrust chamber fuel main valve (43) is a two-position three-way valve and comprises an inlet, an outlet A and an outlet B;
the fuel primary pump (41) and the fuel secondary pump (42) are coaxially arranged with the main turbine (12);
the inlet of the primary fuel pump (41) is communicated with the outlet of the fuel storage tank, and the outlet of the primary fuel pump (41) is connected with the inlet of the secondary fuel pump (42) through a fourth pipeline (45);
the outlet of the secondary fuel pump (42) is connected to the second line (36) via a fifth line (47) at a point downstream of the outlet of the third non-return valve (33), the second non-return valve (46) being arranged in the fifth line (47);
the outlet of the primary fuel pump (41) is also connected to the third line (37) by a sixth line (48) between the outlet B of the generator fuel valve (34) and the inlet of a fourth non-return valve (35), the first non-return valve (44) being located in the sixth line (48);
the outlet of the primary fuel pump (41) is also connected with the main fuel inlet of a thrust chamber (13) through a seventh pipeline (49), and a main fuel valve (43) of the thrust chamber is arranged in the seventh pipeline (49);
the starting system comprises a high-pressure gas supply device, a high-pressure gas one-way valve (51), an oxygen pre-pressurizing pump (52), an oxygen pre-pressurizing turbine (53), a switching valve (54), a liquid oxygen one-way valve (55) and a blender (56);
the high-pressure gas supply device is connected with an inlet of the oxygen pre-pressurizing turbine (53) through an eighth pipeline (57), and the high-pressure gas one-way valve (51) is arranged on the eighth pipeline (57);
the oxygen precompression pump (52) and the oxygen precompression turbine (53) are coaxially arranged; the inlet of the oxygen preloading pump (52) is communicated with the outlet of the oxidant storage tank, and the outlet of the oxygen preloading pump (52) is connected with the inlet of the oxygen main pump (21) through a ninth pipeline (58); the blender (56) is disposed on a ninth conduit (58);
the inlet of the oxygen pre-pressurizing turbine (53) is connected with the first pipeline (23) through a tenth pipeline (59), and the connecting position is between the outlet of the oxygen main pump (21) and the inlet of the liquid oxygen main valve (22); the outlet of the oxygen pre-pressurizing turbine (53) is connected with a blender (56) through an eleventh pipeline (60);
the liquid oxygen check valve (55) is arranged in a tenth pipeline (59);
the switching valve (54) is a two-position three-way valve and comprises an inlet, an outlet A and an outlet B, the switching valve (54) is connected into the eleventh pipeline (60) through the inlet and the outlet A, and the outlet B is communicated with the outside.
2. The multiple start liquid oxygen kerosene engine of a gas driven precompression turbine as claimed in claim 1, wherein:
a first throttling ring (61) is further arranged on a pipeline between the outlet of the ignition agent supply valve (32) and the inlet of the third one-way valve (33).
3. The multiple start liquid oxygen kerosene engine of a gas driven precompression turbine as claimed in claim 2, wherein:
and a second throttling ring (62) is further arranged on a pipeline between the outlet of the fourth one-way valve (35) and the ignition inlet of the thrust chamber (13).
4. The multiple start liquid oxygen kerosene engine of a gas driven precompression turbine as claimed in claim 3, wherein:
and a third throttling ring (63) is further arranged on a pipeline between the outlet of the primary fuel pump (41) and the inlet of the first one-way valve (44).
5. The multiple start liquid oxygen kerosene engine of a gas driven precompression turbine as claimed in claim 4, wherein:
and a fourth throttling ring (64) is further arranged on a pipeline between the outlet of the third one-way valve (33) and the generator fuel valve (34).
6. The starting method of the liquid oxygen kerosene engine for starting for multiple times by using the gas-driven pre-compressed turbine is characterized by comprising the following steps of:
(1) liquid oxygen and fuel fill
Before the engine is started, the liquid oxygen system is precooled and filled, and the oxidant is discharged to the outside from a liquid oxygen main valve (22);
the fuel system is vacuumized and filled with fuel, and the fuel is discharged to the outside from a fuel main valve (43) of the thrust chamber;
(2) ignition agent charge
Starting, the high-pressure gas extrudes an igniter starting box (31), simultaneously opens an igniter supply valve (32), and the igniter fills an ignition path of the fuel gas generator (11) and an ignition path of the thrust chamber (13) through a third one-way valve (33), a generator fuel valve (34) and a fourth one-way valve (35);
(3) after the ignition path of the thrust chamber (13) is filled with the ignition agent, a control instruction is sent to the switching valve (54), and the outlet of the oxygen pre-pressurizing turbine (53) is communicated with the outside;
(4) supplying high-pressure gas, wherein the gas enters a gas static cavity of an oxygen pre-pressurizing turbine (53) through a high-pressure gas one-way valve (51), the oxygen pre-pressurizing turbine (53) is driven to do work, so that a positive lift is generated by an oxygen pre-pressurizing pump (52), and pressurized liquid oxygen is discharged from a discharge port of a liquid oxygen main valve (22);
(5) the liquid oxygen main valve (22) is opened, and liquid oxygen is filled in an oxygen head cavity of the fuel gas generator;
(6) the generator fuel valve (34) is opened, the igniter enters the gas generator (11) at a certain flow rate, the gas generator (11) generates gas, and the gas drives the main turbine (12) to work;
(7) along with the increase of the rotation speed of the main turbine (12), the oxygen main pump (21), the fuel primary pump (41) and the fuel secondary pump (42), when the pressure behind the fuel secondary pump (42) is increased to be larger than the opening pressure of the second check valve (46), kerosene enters a generator fuel path, the igniter starting box (31) stops supplying the igniter, and then the igniter extrudes gas to remove gas;
when the pressure after the fuel primary pump (41) rises to be larger than the opening pressure of the first one-way valve (44), the kerosene enters the ignition path of the thrust chamber (13);
when the pressure behind the oxygen main pump (21) is greater than the opening pressure of a liquid oxygen one-way valve (55) of a driving path of the oxygen pre-pressurizing turbine (53), liquid oxygen enters a liquid static cavity of the oxygen pre-pressurizing turbine (53) and drives the oxygen pre-pressurizing turbine (53) to work together with high-pressure gas;
(8) the high-pressure gas supply is cut off, and the high-pressure liquid oxygen behind the oxygen main pump (21) continues to drive the oxygen pre-pressurizing turbine (53) to do work;
(9) the switching valve (54) is reset, high-pressure liquid oxygen after the oxygen main pump (21) enters a blender (56) after the oxygen pre-pressurizing turbine (53) is driven, and enters an inlet of the oxygen main pump (21) after being blended with liquid oxygen after the oxygen pre-pressurizing pump (52);
(10) determining the opening time of a fuel main valve (43) of the thrust chamber according to the filling time of the thrust chamber (13), and igniting the thrust chamber (13) after the residual power of a main turbine (12), an oxygen main pump (21), a fuel primary pump (41) and a fuel secondary pump (42) is enough to generate positive feedback on the power of the main turbine (12), the oxygen main pump (21), the fuel primary pump (41) and the fuel secondary pump (42);
(11) the engine gradually enters the primary operating condition.
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| CN111720238B (en) * | 2019-07-03 | 2021-08-10 | 西安航天动力研究所 | Liquid oxygen expansion cycle-based depth variable-thrust multi-start liquid rocket engine |
| CN111720239B (en) * | 2019-07-03 | 2021-05-25 | 西安航天动力研究所 | Liquid rocket power system capable of starting liquid rockets for multiple times with variable-depth pushing |
| CN111502865B (en) * | 2020-04-16 | 2021-05-04 | 西安航天动力研究所 | Test run method of open-cycle liquid oxygen kerosene engine system |
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| CN112555056B (en) * | 2020-12-02 | 2022-05-10 | 西安航天动力研究所 | Afterburning circulating liquid engine core system thermal test device and parameter coordination method |
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| CN114458476A (en) * | 2020-12-28 | 2022-05-10 | 北京天兵科技有限公司 | Cold air driving forced starting system and method for liquid rocket engine |
| CN113958425B (en) * | 2021-12-20 | 2022-05-10 | 西安航天动力研究所 | Open-cycle liquid oxygen kerosene engine system and using method thereof |
| CN116480488A (en) * | 2023-06-19 | 2023-07-25 | 西安航天动力研究所 | Self-adaptive starting afterburning cycle engine system and starting method thereof |
| CN117759458A (en) * | 2024-02-22 | 2024-03-26 | 西安航天动力研究所 | start control method and device for oxygen-enriched afterburning engine and computer storage method |
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| RU2523084C1 (en) * | 2013-03-20 | 2014-07-20 | Государственное научное учреждение Всероссийский научно-исследовательский институт электрификации сельского хозяйства Российской академии сельскохозяйственных наук (ГНУ ВИЭСХ Россельхозакадемии) | Method and device for micro gas turbine starting and cooling by starting compressor with air valve |
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